Safran Aircraft Engines

Fabien Stéphane Garnier

Arnaud Lasantha Genilier

Vincent François Georges Millier

Pierre Jean-Baptiste Metge

Nicolas Ovaere

François Pierre Michel Comte

Stéphane Pierre Guillaume Blanchard

Benoit Guillaume Silet

Sébastien Vincent François Dreano

Alexandre Corsaut

Ghislain Hervé Abadie

Mickaël Voiron

Thibaud Louis Zaia

Driss Karim

Pierre Antony

A ventilation ring for a bearing support member of an aircraft turbine engine includes two or more tubular walls and one or more spacer walls. The two or more tubular walls extend opposite each other, and one or more of the tubular walls includes a main portion and a base, the base having a thickness greater than a thickness of the main portion. The one or more spacer walls connect the two or more tubular walls. The one or more spacer walls have one or more apertures extending into the base and a rim around the aperture. An entirety of the rim has a thickness greater than a thickness of the spacer wall at a distance from the rim.

Ventilation ring for the rear bearing support member of an aircraft turbine engine

A dynamic seal for a turbomachine, including a fixed portion provided with at least one abradable wear part and a movable portion including at least one lip arranged to interact with the at least one wear part during the rotation of the movable portion. The wear part includes a structure forming cavities arranged in one or more series such that, in each series, the cavities of this series are superposed radially with respect to the central axis, the structure being configured to limit or prevent the circulation of gas between each pair of radially adjacent cavities. A method for the additive manufacture of the fixed portion of this dynamic seal is also described.

Dynamic seal for a turbomachine comprising a multi-layer abradable part

A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.

Turbine housing cooling device

Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

Turbomachine output bearing support

A device () for cooling an annular outer turbine casing () includes at least one circumferentially extending tube () having an air inlet intended for conveying cooling air, the tube having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged radially opposite each other, an air inlet manifold (), the inlet of the tube opening into the manifold, the tube () including at least one intermediate wall extending over a circumferential portion of the tube from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.

Device for cooling an annular outer turbine casing

The invention relates to a lubrication device () for a turbo machine, comprising:

Lubrification device for a turbo machine

The invention relates to a pressurized-air supply unit for an air-jet cooling device cooling an outer casing of a turbomachine turbine. This unit is notable in that it is monobloc, in that it comprises: &#x2014;a body which has an interior wall provided with air-ejection perforations, an exterior wall and outlet ducts which are configured to be coupled to cooling lines of the cooling device, &#x2014;an elbowed air-conveying pipe coupled by its outlet opening to said exterior wall of the body, and in that said unit comprises at least one air-distribution partition, arranged in the outlet opening and connecting the internal face of the portion of the air-conveying pipe that is situated facing the body to the internal face of the opposite portion of the air-conveying pipe.

Growing community of inventors

Moissy-Cramayel, France

Fabien Stéphane Garnier